Monoplane.



S. F. NAUGHTON.

MONOPLANE.

APPLICATION FILED fill. 12. H15

1 176,593. Patented Mar. 21, 1916.

suit I.

s. r. NAUGHETON.

MONOYLANE.

APPLICATION HLID III. 12. "IL

Patented Mar. 21, 1916.

3 lNHN-INEU 2.

HI mu l! mum-Ar" cu. UKININGI'DN In c.

S. F. NAUGHTON.

Patentul Mar. 21, 1916. I

3 SHEETS-SHEET 3.

STEPHEN F. NAUGHTON. OF THE UNITED STATES NAVY.

MONOPLANE.

Specification of Letters Patent.

Patented Mar. 21. 19.16.

Application filed February 12, 1915. Serial No. 7.890.

To all whom. it may concern Be it known that I. S'rsrnaa F. lanoli- 'ro.\, of the United States Navy, a citizen of the United States, residing at New York. in the county of New York, and State of New York. have invented new and useful Improvements in Monoplanes, of which the fol owing is a specification.

This invention relates to monoplanes, and its object is to provide structural features increasing the strength. durability and general oiliciency of this class of air craft.

The invention is illustrated in the accompanying drawings, in which Figure 1 is a side elevation of my improved monoplane. Fig. 2 is a front elevation of the same. Fig. 3 is a top plan view, partially broken awav. Fig. 4 is a vertical transverse section through the fuselage. Fi 5 is a view of the control device. Fig. 6 1S a sectional side elevation of a portion of the landing gear. Fig. 7 is an enlarged detail view, partly in section, showing a bracing construction. Figs. 8 and 9 are detail views of clips or guv wire connections. Fig. 10 is a sectional view taken substantia ly on the line 10-10 of Fig. 9.

Referrin to the drawing. 1 designates the body 0 the machine, winch is of stream line form, and provided with a cock pit or compartment 2 to receive the motor and aviator and one or more passengers. The body has an empennage or tail extensions 3 carrying fixed vertical stability fins 4 and fixed horizontal stability fins 5. Hinged or pivoted to the rear end of the body in line with the vertical tins is a vertical rudder (l, and hinged or pivoted to the rear edges of the horizontal fins are the sections 7 of a double or two-part horizontal rudder, which rudders are controlled by a steering gear located within the body as hereinafter fully described.

The body is constructed of a suitable frame work over which is placed a covering of metal fabric or other suitable material. This frame work includes longitudinal spars 8 connected by suitable vertical and horizontal struts or cross pieces 9, the frame work being reinforced by stays 10. The stays 10 are secured to and extend from suitable clips or brackets fastened between the longitudinal spars and struts or cross pieces, which braces may be of the three-arm type designated by 11 in Fig. 8 or the four-arm type designated by 12 in Fig. 9, according to position and the number of stays and struts employed, each bracket having an opening 13 or the passage of a dowel or fastening bolt 14 connecting the same with the strut to the longitudinal spar, as shown in Fig. 7, the arms of the bracket being arranged at proper angles and a iortured for the reception of the ends of the stays which are suitably tied or otherwise fastened thereto. By this construction, and by the use of other proper bracing at desired points when ltltlililoti, a strong and durable type of stream ine body is provided.

he supporting surface of the machine comprises a plane composed of laterally extending wins 11' fastened at their inner ends to the aid and reinforced from the body and from each other by upper and lower braces 16 enga ing suitable anchor stail's or brackets 17. he wings may be of any ordinary or preferred general struc ture and curvature and are provided with adjustable tips or ailerons 18. These tips or ailerons are connected above the plane for movement in unison by a cord or cable 10 extending over suitable guide pullovs .20. and said tips or ailerons are ms iectivoly attached below the plane to cab es or cords 21 and 22 passing over suitable guide pulleys 28 to a point within the cock pit. where they are connected with a control device as hereinafter described. It will be observed that the tips are coupled for movement in unison, one movin upwardly while the other moves downward y, and that said tips are so uirated from the wings along the di gona division lines SH to swing on oblique rearwardly converging axes. so that when the tip at the low side of the unbalanced machine is depressed for a lifting action it will also assume an angular position .to the line of flight which diminishes the resistance of the wing and top to forward travel. On the other hand, the wing at the high side which is swung upwardly to dopress that side will be shifted at such an angle to the line of flight as to increase the resistance of said win to forward travel thus preventing the high side from traveling at a faster rate of speed than the low side and avoiding fore-and-aft oscillation of the machine on its vertical axis during balancing or banking operations.

Arranged within the forward portion of the body 1 is a driving motor 25 which communicates motion to a forward or tractor tit) ii I) propeller 26. They motor shown in the present instance is of the water-cooled type, and its water jacket 27 is connected by flow pipes or tubes 28 with radiators 29 at the opposite sides of the body. These radiators are rovided with laterally extendin vanes or r1 s 30, which project outward] t rou h discharge openings 30' in the si es of t e body and operate in the forward travel of the machine to produce a partial vacuum or suction, whereby a draft of cooling air is drawn inwardly through a suction opening 31 in the bowof the body and discharged through the openings 3 \Vithin this opening 31 is a spider or skeleton bearing 32 in which the propeller shaft is journaled. The vanes 30 lie in the ath of the air from the propeller so that t ieir suction producing action is increased to a material degree. The means for adjusting and controlling the rudder and wing tips comprises a lever 33 pivoted to swing laterally at its lower end on a pivot mem er 34 on which are loosely journaled guide or direction pulleys 35 and 36. At its upper end the lever is provided with a bearing 37 for a shaft 38 provided with a hand wheel 39 and a drum or pulley 40. Attached to the lever at the point 41 are the forward ends of cables 42 which pass rearwardly over suitable guides and are coupled to the rudder 6 whereby the latter may be adjusted through lateral movements of the lever 33 on its axis 34. The inner ends of the cords or cables 22 pass around the ulleys 35 and 36 and are arranged to win in opposite directions about the drum 40, whereby the ailerons 18 may be adjusted in an obvious manner. A second lever 43 is arranged within the cock pit and is coupled by a suitable connection or connections 44 with the horizontal rudder members 7 whereby the same may be adjusted.

The machine embodies a landing gear of improved construction including front cush ioned wheels 44 and skids or runners 45 and a rear skid or fender 46. The skids or runners 45 are arranged at the opposite sides of the fore-part'of the body and are rigidl connected therewith by bracket rods or tu es 47 and reinforced by braces 48. The wheels 44 are arranged in pairs at opposite sides of the body, each pair being carried by a wheel support consisting of a triple fork 49, the arms of which support a transverse axle in 50 on which the wheels 44 are mounted within the outer fork spaces. Journaled upon the axle within the middle fork space isa friction wheel or roller 51 over which passes a rubber or other elastic band 52 secured in front and rear of said friction wheel to the skid 45. As shown, the skids extend beneath the friction wheels or spools 51 which are held between the skids and the elastic bands 52, whereby the fork 49 and wheels 44 are permitted to have vertical movement relative to the skids and are given a resultant cushioning action through the elasticity of the rubber backing bands 52. Each fork 49 has an upwardl extendin guide stem 53 which is movable vertica ly within a guide tube or sleeve 54 fixed to the adjacent side of the body. Inclosed within the body is a coiled cushioning spring 55 backing the stem 53 and sustaining the sleeve therefrom, and inclosing the outer ortions of the stem and sleeve is a cushloning spring 56 bearing against abutment shoulders 57 and 58, by which additional cushioning means are provided for sustaining and cushioning the weight of the machme in launching and landing actions and in traveling over rough ground surfaces. It will be observed that the described construction not only provides a cushioning connection between the wheels and skids, but also between the wheels and body, giving a maximum cushioning action.

t will be evident from the foregoing that my invention provides a monoplane which, while simple of construction, embodies oints of superiority in various respects, including means for securing an exhaust of the hot air from the motor compartment, means for balancing and banking the machine with eliiciency and means for securing a. cushioning action which has a high range of flexibility and capacity to resist strains without damage.

I claim In a flying machine, the combination of a hollow body or nacelle having a suction opening in the front portion and sets of discharge openings in the side portions of its bow, a-supporting surface carried by the body, suitable steerin and. stabilizing means, a motor positioned in the bow ofthe body and having its shaft extending forwardly throu h the suction opening, radiators at the sides of the bow of the body having suction producin vanes projecting outwardly through said ischarge openin s, so as to lie in the path of the wind and irectly in the path of the air from the propeller, whereby a suction is produced'within the bow to draw cooling drafts of air there- 1nto through the suction opening and discharge the same through the said side discharge openmgs, and conductors extending between and connecting the radiators with the water jacket of the motor.

In testimony whereof I aflix my signature in presence of two witnesses.

STEPHEN F. NAUGHTON.

Witnesses:

James T. ALEXANDER, GEO. C. TASKER.

copies el this patent may be obtained for five cents each. by sddresslng the "Commissioner 0! Istents, Wsshinzton, D. 0." 

